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一、引言固体火箭发动机装药与内弹道的优化设计和性能予示都需要准确计算推进剂在发动机实际工作条件下的燃速,对于内孔燃烧的装药主要就是侵蚀燃速。计算推进剂的侵蚀燃速一般有三种方法可供选择:
I. INTRODUCTION The optimal design and performance of solid rocket motor charge and internal ballistic trajectory are required to accurately calculate the burning rate of the propellant under the actual working conditions of the engine. The charge of the bore combustion is mainly the erosion burning rate. There are generally three ways to calculate the erosion rate of a propellant: